EP 0760051 B2 20020109 - AIRFOIL WITH DUAL SOURCE COOLING
Title (en)
AIRFOIL WITH DUAL SOURCE COOLING
Title (de)
LEITSCHAUFELKÜHLUNG MIT DOPPELQUELLE
Title (fr)
VOILURE A SYSTEME DE REFROIDISSEMENT A DEUX SOURCES
Publication
Application
Priority
- US 9501167 W 19950126
- US 23448894 A 19940428
Abstract (en)
[origin: WO9530069A1] An airfoil (42) for a gas turbine engine (10) having an airfoil portion (52) with a leading and a trailing edge (60, 62) includes dual pressure source cooling. The trailing edge (62) of the airfoil (42) includes an internal trailing edge passage (78) and the leading edge (60) includes an internal leading edge passage (64). Compressor bleed air at higher pressure is channeled through the leading edge passage (64) whereas compressor bleed air at lower pressure is channeled through the trailing edge passage (78). The higher internal pressure in the leading edge (60) ensures that the inward flow of products of combustion does not occur.
IPC 1-7
IPC 8 full level
CPC (source: EP US)
F01D 5/187 (2013.01 - EP US); F01D 9/065 (2013.01 - EP US); F01D 11/001 (2013.01 - EP); F01D 11/04 (2013.01 - EP); F05D 2240/121 (2013.01 - EP); F05D 2240/122 (2013.01 - EP); F05D 2260/201 (2013.01 - EP US); Y02T 50/60 (2013.01 - EP US)
Citation (opposition)
Opponent :
US 3742706 A 19730703 - KLOMPAS N
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
WO 9530069 A1 19951109; DE 69503628 D1 19980827; DE 69503628 T2 19990325; DE 69503628 T3 20020814; EP 0760051 A1 19970305; EP 0760051 B1 19980722; EP 0760051 B2 20020109; JP 3761572 B2 20060329; JP H09512604 A 19971216; US 5498126 A 19960312
DOCDB simple family (application)
US 9501167 W 19950126; DE 69503628 T 19950126; EP 95909375 A 19950126; JP 52818495 A 19950126; US 23448894 A 19940428